Half split hierarchical S-shaped air inlet channel design method

Abstract

The invention discloses a half split hierarchical S-shaped air inlet channel design method. First, by use of two stationary blade row mean camber line design for reference, two-dimensional half split design idea is used, dimensionless parameter ''load coefficient'' ''expansion coefficient'' control of air inlet channel normal and axial pressure distribution is proposed, a two-dimensional wall surface molded line of an S-shaped air inlet channel is designed, and a two-dimensional wall surface geometric parameterized model is established; total pressure recovery coefficient is used as an optimization objective, and by combination of genetic algorithm and an S-shaped air inlet channel modelling program, the two-dimensional parameterized model is optimized; by use of three-dimensional hierarchy design idea and by introduction of dimensionless parameter ''distribution coefficient'', an S-shaped air inlet channel three-dimensional geometric model is further obtained by determination of center line along the distance; and finally, the total pressure recovery coefficient and outlet distortion are used as an optimization objective, the genetic algorithm is used for multi-objective optimization of the model, and by discuss of physical relationship of the parameters and the air inlet total channel pressure loss and the outlet distortion, an S-shaped air inlet channel with better aerodynamic performance can be obtained.

Description

technical field [0001] The invention relates to a design method of a "half-layered" S-shaped air inlet. Aiming at the problems of S-shaped inlet flow loss and outlet distortion caused by the large curvature change of the wall surface, the design idea of ​​"two-dimensional split in half" and "three-dimensional layered" was adopted to establish a geometric parameter model of the wall and develop the S-shaped inlet with better aerodynamic performance. Shaped inlet design method. Background technique [0002] The Langley Research Center of NASA in the United States proposed the concept of BWB Aircraft (Blended Wing Body Aircraft) in the 1990s. Due to the small wetted area of ​​the wing-body fusion aircraft, friction can be achieved under the premise of meeting the required volume. reduction in resistance. Compared with the traditional layout, the wing-body fusion layout aircraft has larger load capacity, higher lift-to-drag ratio and lower fuel consumption rate, and its econom...

AI Technical Summary

Problems solved by technology

Since the largest separation area in the S-shaped inlet occurs at the place of large curvature and large diffusion, the curvature of the S-shaped pipe wall surface will lead to an unfavorable local pressure gradient. However, the traditional S-shaped inlet design is to directly introduce the law of flow area into the centerline equation to establish a three-dimensional model. Therefore, this design method cannot effectively establish the dynamics of the wall curvature and wall pressure distribution of the large-curvature S-shaped inlet. academic associations, the design results are often uncertain and limited

Images